Aerospace Science and Technology最新文献_第8页

Sensor importance-aware dual-branch cGAN: High-fidelity synchronous prediction of flame-schlieren images for scramjet flow fields 传感器重要性感知双分支cGAN：超燃冲压发动机流场火焰纹影图像的高保真同步预测

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-01-08 DOI: 10.1016/j.ast.2026.111661

YuXin Yang , Ye Tian , Mingming Guo , Zekai Lu , Liao Zhou , Yajun Hu

The flow field in a scramjet combustor features strong coupling of shock waves, chemical reactions, and vortex structures, presenting inherent challenges of unsteadiness and nonlinearity for real-time monitoring and dynamic prediction—key scientific issues restricting engine performance optimization. Existing deep learning-based methods suffer from two critical limitations: single-modal reconstruction fails to comprehensively characterize flow field evolution, and redundant sensor deployment leads to inefficient monitoring without considering feature contribution differences. To address these, we propose a sensor importance analysis-based conditional generative adversarial network (SI-cGAN) with rigorous scientific design for high-fidelity synchronous reconstruction of schlieren and flame chemiluminescence images. The method integrates SHAP analysis—rooted in game theory—to quantify the contribution of 32 wall pressure sensors, enabling data-driven optimization of sensor selection via feature ranking. The SI-cGAN adopts an encoder-decoder architecture to learn the nonlinear mapping from pressure data to flow field images, with a dual-branch generator tailored for synchronous generation of dual-modal images and a composite loss function (adversarial loss+L1 reconstruction loss) ensuring physical consistency of flow structures. Experimental results validate the scientific effectiveness of the method: on the test set with 8 key sensors (25% of the full array), the Peak Signal-to-Noise Ratio (PSNR) reaches 24.21 dB for schlieren images and 25.61 dB for flame images, while the Structural Similarity Index (SSIM) of flame images retains 97.7% (0.9276) of the full-sensor performance with only 3.1% degradation. This study not only provides a quantitative scientific basis for optimizing sensor layout in scramjets but also establishes an efficient technical paradigm for multimodal visual monitoring of complex turbulent combustion systems, bridging the gap between sparse sensing and high-fidelity flow field prediction.

超燃冲压发动机燃烧室内的流场具有激波、化学反应和涡流结构的强耦合特性，对实时监测和动态预测提出了非定常和非线性的固有挑战，这是制约发动机性能优化的关键科学问题。现有的基于深度学习的方法存在两个关键的局限性：单模态重建无法全面表征流场演化，冗余的传感器部署导致监测效率低下，而没有考虑特征贡献差异。为了解决这些问题，我们提出了一种基于传感器重要性分析的条件生成对抗网络（SI-cGAN），该网络具有严格的科学设计，用于纹影和火焰化学发光图像的高保真同步重建。该方法集成了基于博弈论的SHAP分析，量化了32个壁面压力传感器的贡献，通过特征排序实现了数据驱动的传感器选择优化。SI-cGAN采用编码器-解码器架构来学习压力数据到流场图像的非线性映射，具有专为同步生成双模态图像而定制的双支路生成器和复合损失函数（对抗损失+L1重建损失），确保了流结构的物理一致性。实验结果验证了该方法的科学有效性：在8个关键传感器（占全阵列的25%）的测试集上，纹影图像的峰值信噪比（PSNR）达到24.21 dB，火焰图像的峰值信噪比（PSNR）达到25.61 dB，而火焰图像的结构相似指数（SSIM）保持了全传感器性能的97.7%(0.9276)，仅下降3.1%。该研究不仅为超燃冲压发动机传感器布局优化提供了定量的科学依据，而且为复杂湍流燃烧系统的多模态视觉监测建立了有效的技术范式，弥补了稀疏感知与高保真流场预测之间的差距。

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引用次数: 0

Joint multi-target detection and single-target tracking framework for vehicles tracking based on UAV 基于无人机的车辆联合多目标检测与单目标跟踪框架

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-01-07 DOI: 10.1016/j.ast.2026.111625

Jiayu She , Yanfang Liu , Rui Zhou , Naiming Qi

Currently, most multi-object tracking methods based on Tracking-by-Detection require detecting objects in every frame, demanding substantial computational resources and limiting real-time performance. To address this, we propose a Joint Multi-object Detection and Single-object Tracking (JMDST) framework for ground vehicle tracking from UAV perspective. JMDST consists of two branches: a detection branch and a tracking branch. The detection branch operates periodically to identify all targets in the image at specific intervals, handling targets that dynamically enter or leave the scene. At other times, the tracking branch performs single-object tracking: it predicts target locations, crops small-sized images around these regions, and accurately localizes the targets within these small-sized images to maintain continuous tracking. We propose the Feature Encoding and Location Network (FELNet) to localize targets and extract features within the small-sized images. A dense random sampling strategy and cross-correlation operations are incorporated to enhance the effectiveness of the embedding features. Furthermore, we introduce the Mamba Sequence Feature Prediction (MSFP) module, based on the Mamba network, which predicts the current feature encoding of a target using its historical feature sequence. This enhances robustness to appearance changes and improves trajectory matching accuracy. We evaluate JMDST against state-of-the-art multi-object tracking methods on three UAV-view datasets: MDMT, UAVDT, and VisDrone2019. Experimental results show that JMDST achieves competitive tracking performance with the highest inference speeds on all three datasets, reaching FPS values of 18.9, 26.6, and 18.6, respectively.

目前，大多数基于检测跟踪的多目标跟踪方法需要在每一帧中检测目标，这需要大量的计算资源，并且限制了实时性。为了解决这一问题，我们提出了一种用于无人机视角下地面车辆跟踪的联合多目标检测和单目标跟踪（JMDST）框架。JMDST由两个分支组成：检测分支和跟踪分支。检测分支周期性地工作，以特定的时间间隔识别图像中的所有目标，对动态进入或离开场景的目标进行处理。其他时候，跟踪分支进行单目标跟踪：预测目标位置，在这些区域周围裁剪小尺寸图像，并在这些小尺寸图像内精确定位目标，保持连续跟踪。我们提出了特征编码和定位网络（FELNet）来定位目标和提取小尺寸图像中的特征。为了提高嵌入特征的有效性，采用了密集随机采样策略和相互关联操作。此外，我们还介绍了基于曼巴网络的曼巴序列特征预测（Mamba Sequence Feature Prediction， MSFP）模块，该模块利用目标的历史特征序列来预测目标的当前特征编码。这增强了对外观变化的鲁棒性，提高了轨迹匹配精度。我们在三个无人机视图数据集（MDMT、UAVDT和VisDrone2019）上对JMDST与最先进的多目标跟踪方法进行了评估。实验结果表明，JMDST在所有三个数据集上都以最高的推理速度获得了具有竞争力的跟踪性能，FPS值分别达到18.9、26.6和18.6。

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引用次数: 0

Multi-fidelity surrogate optimization of an electrothermal ice protection system for in-flight anti-icing 飞机防冰电热防冰系统的多保真度代理优化

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-01-07 DOI: 10.1016/j.ast.2026.111640

Maziyar Ghasemnezhad, Esmaeil Esmaeilifar, Rho Shin Myong

This study proposes a novel multi-fidelity surrogate optimization (MFSO) framework for evaluating and optimizing an electrothermal ice protection system for in-flight anti-icing. This approach effectively integrates high-fidelity and low-fidelity simulations to significantly reduce the number of training samples required to train an accurate surrogate model, thereby lowering computational costs without compromising accuracy. The surrogate model was constructed via proper orthogonal decomposition (POD) and multi-fidelity Gaussian process regression (MFGPR). To perform high-fidelity simulations of the electrothermal anti-icing process, a unified finite volume framework was employed. This framework efficiently combines several in-house solvers, including a compressible Navier–Stokes–Fourier (NSF) airflow solver, an Eulerian droplet impingement solver, a partial differential equation (PDE)-based ice accretion solver, and a multilayer heat conduction solver. The optimization framework minimizes total electric power consumption while satisfying regime-specific constraints in both running-wet and evaporative modes. The search for optimal heater power distributions is guided by the mesh adaptive direct search (MADS) algorithm. Our findings show that the multi-fidelity surrogate model reduces training cost by 75% by lowering the number of required high-fidelity simulations from 400 in the single-fidelity approach to 100. The optimization results achieved up to 38.5% reduction in total electric power consumption for the running-wet regime and 40% for the evaporative regime under representative operational constraints for the NACA0012 airfoil.

本研究提出了一种新的多保真度替代优化（MFSO）框架，用于评估和优化飞行防冰电热防冰系统。该方法有效地集成了高保真度和低保真度模拟，显著减少了训练精确代理模型所需的训练样本数量，从而在不影响准确性的情况下降低了计算成本。通过适当正交分解（POD）和多保真高斯过程回归（MFGPR）构建代理模型。为了对电热防冰过程进行高保真模拟，采用了统一的有限体积框架。该框架有效地结合了多个内部求解器，包括可压缩的Navier-Stokes-Fourier （NSF）气流求解器、欧拉液滴撞击求解器、基于偏微分方程（PDE）的冰积求解器和多层热传导求解器。优化框架最大限度地减少总电力消耗，同时满足运行湿和蒸发模式下的特定状态约束。采用网格自适应直接搜索（MADS）算法对加热器功率分布进行优化搜索。我们的研究结果表明，通过将所需的高保真度模拟次数从单保真度方法的400次减少到100次，多保真度代理模型将训练成本降低了75%。优化结果使NACA0012翼型在具有代表性的运行约束条件下，湿转工况的总耗电量减少38.5%，蒸发工况的总耗电量减少40%。

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引用次数: 0

Dual-actuated fuel valve based on piezoelectric stack and stepper motor with active decoupling control for combustion oscillations 基于压电堆和步进电机的双驱动燃油阀燃烧振荡主动解耦控制

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-01-07 DOI: 10.1016/j.ast.2026.111658

Pengda Ren , Bin Wang , Zhifeng Ye

Lean premixed combustion offers advantages such as low nitrogen oxide emissions and high combustion efficiency, but it is more prone to inducing coupled oscillations in combustion chambers. The resulting intense pressure fluctuations can degrade aeroengine performance and even seriously compromise flight safety. Therefore, active decoupling control methods for combustion oscillations have become a critical research focus. To address the challenge, this study proposed a bilateral direct‑drive fuel valve actuated by a stepper motor and a piezoelectric actuator, along with an active decoupling control algorithm. A nonlinear combustion oscillation model was established, including the flame model, the thermo‑velocity model, and the thermo‑pressure model, to simulate the decoupling effect of the valve based on a phase‑shift controller and the proposed state‑observer‑based phase‑shift controller(SO-PSC). Key parameters influencing decoupling performance, such as observation window width β and amplitude‑variation‑rate feedback gain K_ref were analyzed, and the control performance was compared with mainstream controllers. The results indicated that the bilateral direct‑drive valve and its controller achieve effective decoupling of combustion oscillations, outperforming control methods including H∞, STR, and PID controllers. Optimal performance is achieved by setting β to 3.6 and K_ref to 82, which yields a 72.6% reduction in combustion oscillation and a decay time of 0.037 s.

贫预混燃烧具有氮氧化物排放少、燃烧效率高的优点，但更容易在燃烧室内诱发耦合振荡。由此产生的强烈压力波动会降低航空发动机的性能，甚至严重危及飞行安全。因此，燃烧振荡的主动解耦控制方法已成为一个重要的研究热点。为了解决这一挑战，本研究提出了一种由步进电机和压电驱动器驱动的双边直接驱动燃油阀，以及一种主动解耦控制算法。建立了包括火焰模型、热速度模型和热压力模型在内的非线性燃烧振荡模型，模拟了基于相移控制器和基于状态观测器的相移控制器（SO-PSC）的气门解耦效果。分析了影响解耦性能的关键参数，如观测窗宽β和幅值变化率反馈增益Kref，并与主流控制器进行了控制性能比较。结果表明，双向直接驱动阀及其控制器实现了燃烧振荡的有效解耦，优于H∞、STR和PID控制方法。当β值为3.6，Kref值为82时，燃烧振荡降低72.6%，衰减时间为0.037 s。

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引用次数: 0

Inertia parameter identification via neural network and reinforcement learning for combined spacecraft attitude takeover control 基于神经网络和强化学习的航天器姿态接管联合控制惯性参数辨识

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-01-07 DOI: 10.1016/j.ast.2025.111551

Ziyao Geng , Wenlong Lu , Qiang Shen , Shufan Wu , Vladimir Yu Razoumny , Yongchun Xie

The attitude takeover control of the combined spacecraft after capturing the non-cooperative target has become one of the key technologies for on-orbit servicing and maintenance of spacecraft. However, a complete takeover control process necessitates first identifying the inertial parameters of the combined spacecraft and then conducting the attitude takeover control. Yet, the harsh and complex space environment, compounded by significant angular velocity measurement noise, makes such inertia parameter identification extremely difficult, posing formidable challenges to this task. In order to accurately identify the inertia parameter, we propose an LSTM-based neural network inertia parameter identification approach. This approach can complete the identification within several milliseconds while maintaining a lightweight architecture, thereby rendering it more suitable for on-orbit scenarios with constrained resources. A reinforcement learning-based control strategy is proposed for the attitude takeover control of the combined spacecraft. This strategy enables real-time and accurate identification of the inertia parameter and features thoughtfully designed state representations and reward functions that collectively enhance robustness. Extensive experiments are conducted under diverse measurement noise conditions to simulate different on-orbit mission scenarios, and the findings consistently underscore the proposed framework’s performance advantages over existing identification approaches. The RL-based controller demonstrates strong robustness to variations in the inertia parameter, consistently maintaining high-precision attitude control and rapid, stable recovery across different configurations. The simulation results collectively validate the efficacy of the proposed integrated framework. Specifically, the neural network exhibits high accuracy in estimating the combined spacecraft’s inertial parameters, while the RL-based controller achieves precise attitude regulation with minimal overshoot and fast settling times.

组合航天器捕获非合作目标后的姿态接管控制已成为航天器在轨维修的关键技术之一。然而，一个完整的接管控制过程需要首先确定组合航天器的惯性参数，然后进行姿态接管控制。然而，恶劣而复杂的空间环境，加上明显的角速度测量噪声，使得这种惯性参数识别变得极其困难，给这项任务带来了巨大的挑战。为了准确识别惯性参数，提出了一种基于lstm的神经网络惯性参数识别方法。这种方法可以在几毫秒内完成识别，同时保持轻量级架构，从而使其更适合资源受限的在轨场景。提出了一种基于强化学习的组合航天器姿态接管控制策略。该策略能够实时准确地识别惯性参数，并具有精心设计的状态表示和奖励函数，共同增强了鲁棒性。在不同测量噪声条件下进行了大量实验，以模拟不同的在轨任务场景，结果一致强调了所提出的框架相对于现有识别方法的性能优势。基于rl的控制器对惯性参数的变化具有很强的鲁棒性，在不同配置下始终保持高精度姿态控制和快速稳定的恢复。仿真结果验证了该集成框架的有效性。其中，神经网络对组合航天器的惯性参数估计具有较高的精度，而基于rl的控制器以最小的超调量和快速的沉降时间实现了精确的姿态调节。

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引用次数: 0

Towards high-thrust to power hypersonic air-breathing electric propulsion 从大推力到动力高超声速吸气式电力推进

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-01-06 DOI: 10.1016/j.ast.2026.111643

Anmol Taploo, Guru Sankar Duppada, Jake Spinelli, Michael Keidar

This paper presents a detailed assessment of the propellant-less air-breathing plasma thruster with magneto-plasma-dynamic acceleration, designed for sustained operation in the upper mesospheric altitudes (65–120 km) regime. To analyze plasma behavior under different conditions, a combination of Langmuir probe, time-of-flight diagnostics, high-speed imaging, and optical emission spectroscopy was used. Experiments were performed at mass flow rates (10^–7–10^–3 kg/s) and pulse frequencies from 1 to 50 Hz to simulate the relevant conditions (65–120 km). High-speed imaging revealed the dynamics of arc spots and directional plasma jet formation, which were influenced by acceleration voltage and magnetic field strength. Spectroscopy revealed ionization trends, with orders of magnitude increase (∼6.4 × 10⁴) in the emission intensity. Time of flight analysis confirmed high ion velocities (6–60 km/s) consistent with pulsed acceleration, while thrust and thrust-to-power ratio exceeded 1.6 N and 5 N/kW at higher flow rates, thanks to efficient inlet velocity use and reduced flow stagnation. The results support the thruster's potential as a self-sustaining propulsion system for near-surface orbital applications and offer important performance metrics for system optimization.

本文对具有磁等离子体动力学加速度的无推进剂空气呼吸等离子体推进器进行了详细的评估，该推进器设计用于在上层中层高度（65-120公里）持续运行。为了分析等离子体在不同条件下的行为，使用了Langmuir探针、飞行时间诊断、高速成像和光学发射光谱的组合。实验在质量流量（10-7-10-3 kg/s）和脉冲频率（1 ~ 50 Hz）下进行，模拟相关条件（65 ~ 120 km）。高速成像揭示了加速电压和磁场强度对电弧斑和定向等离子体射流形成的影响。光谱学显示出电离趋势，发射强度增加了几个数量级（~ 6.4 × 104）。飞行时间分析证实，高离子速度（6-60 km/s）与脉冲加速度一致，而推力和推功率比在高流速下超过1.6 N和5 N/kW，这得益于有效的入口速度利用和减少了流动停滞。结果支持了推进器作为近地表轨道应用的自我维持推进系统的潜力，并为系统优化提供了重要的性能指标。

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引用次数: 0

Investigation on cooling performance of fuel-cooled integrated flameholder with jet impingement cooling 燃油冷却射流冲击冷却一体化火焰座冷却性能研究

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-01-06 DOI: 10.1016/j.ast.2026.111633

Kailin Jiang, Zongbo Ma, Yuxin Fan

Integrated flameholders are widely used in advanced afterburner. However, as the operating conditions and environments of advanced afterburners become more demanding, the cooling performance of the flameholder is increasingly required. Therefore, a fuel jet impingement cooling scheme for integrated flameholder is proposed in this paper. The cooling mechanism of the fuel-cooled integrated flameholder is investigated by using numerical simulation methods, along with the effect of different inlet conditions on cooling performance of the fuel-cooled integrated flameholder. Furthermore, the orthogonal experimental method is utilized to investigate the priority of the effects of different inlet conditions on the cooling performance. The results show that fuel-cooled flameholder exhibits significantly superior cooling performance compared to air-cooled flameholder, with an increase in the average heat transfer coefficient (

\bar{h}

) of approximately 40 %. The maximum external wall temperature does not exceed 743 K. When equivalence ratio (

Φ

) increases, the lift distance (LD) significantly increases, which greatly improves cooling performance in intersection zone, thereby resulting in a more uniform wall temperature. However, when inlet Mach number (Ma) increases, cooling mechanism exhibiting variations at cooling mechanism transition point (CTP) owing to flow lift, resulting in a slight increase of the temperature gradient in side regions, while cooling efficiency

(η)

remains stable at 46 %. Furthermore, when inlet temperature (T_a) increases, fuel-cooled integrated flameholder maintains excellent heat transfer capability, with cooling efficiency

(η

) improving by 11.7 %. Notably, T_a has the most significant effect, while Ma has the least effect on average external wall temperature (

\overline{T_{o u t}}

) and cooling efficiency

(η

).

集成式火焰座广泛应用于高级加力燃烧室。然而，随着先进加力燃烧室工作条件和环境的要求越来越高，对火焰座的冷却性能也提出了越来越高的要求。为此，本文提出了一种整体式火焰座的燃油射流冲击冷却方案。采用数值模拟的方法，研究了燃料冷却式集成火焰头的冷却机理，以及不同进口条件对燃料冷却式集成火焰头冷却性能的影响。此外，采用正交实验法研究了不同进口条件对冷却性能影响的优先级。结果表明，燃料冷却型火焰的冷却性能明显优于风冷型火焰，平均传热系数（h¯）提高约40%。外墙最高温度不超过743k。当等效比（Φ）增大时，升力距离（LD）显著增大，极大地改善了交叉口区域的冷却性能，从而使壁面温度更加均匀。然而，当进口马赫数（Ma）增加时，由于流动升程的影响，冷却机制转变点（CTP）处的冷却机制发生变化，导致侧区温度梯度略有增大，而冷却效率（η）稳定在46%。此外，当进口温度（Ta）升高时，燃料冷却式集成火焰座仍保持良好的换热性能，冷却效率（η）提高11.7%。值得注意的是，Ta的影响最为显著，而Ma对平均外墙温度（Tout）和冷却效率（η）的影响最小。

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引用次数: 0

Impact of strut clocking on the secondary flows in an aggressive compressor transition duct 支撑时钟对大进位压缩机过渡管道二次流的影响

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-01-06 DOI: 10.1016/j.ast.2026.111652

Zhenliang Liu , Ting Chen , Yadong Wu

With the improving demand for economic performance and environmental protection in commercial aviation, aero-engine companies are focusing on the development of advanced engines with lower fuel consumption, which leads to the evolution of turbofan engines with larger bypass ratio. The aggressive compressor transition duct, characterized by a large radius drop to length ratio, plays a crucial role in large bypass ratio engines, offering significant potential for weight reduction. However, the larger endwall curvature in the aggressive transition duct induces a more complex flow field, with higher pressure gradients and enhanced interactions between the flow field of the compressor outlet guide vane (OGV) and strut. In this study, unsteady Reynolds-averaged Navier-Stokes (URANS) simulations were conducted on aggressive transition duct models featuring three clocking positions, with ΔR/L = 0.5. The secondary flow system in the duct, which presented significant damage to outflow uniformity, consisted of OGV corner vortex, horseshoe vortex, strut-hub corner separation vortex, strut trailing edge vortex pair, and hub boundary layer separation. The secondary flow system was influenced by strut clocking position through modulating strut-hub corner separation vortex. Frequency spectra and proper orthogonal decomposition (POD) analysis revealed the dominant modes and frequencies, with clocking position-dependent frequency peaks and broadband features, highlighting the potential to eliminate fixed flow frequencies and mitigate forced vibrations through optimized clocking strategies.

随着商用航空对经济性和环保性要求的提高，航空发动机企业将重点放在开发低油耗的先进发动机上，这导致了大涵道比涡扇发动机的发展。进气式压气机过渡管道的特点是半径降长比大，在大涵道比发动机中起着至关重要的作用，具有显著的减重潜力。然而，侵略性过渡管道中较大的端壁曲率会导致更复杂的流场，压力梯度更高，压气机出口导叶与支板流场之间的相互作用增强。本研究对具有三个时钟位置的冲击过渡管道模型进行了非定常reynolds -average Navier-Stokes （URANS）模拟，其中ΔR/L = 0.5。支板转角涡、马蹄形涡、支板-轮毂转角分离涡、支板尾缘涡对和轮毂边界层分离构成了支板内二次流系统，对出口均匀性破坏较大。通过调节支杆-轮毂转角分离涡来影响支杆时钟位置对二次流系统的影响。频谱和适当的正交分解（POD）分析揭示了主导模式和频率，具有与时钟位置相关的频率峰值和宽带特征，强调了通过优化时钟策略消除固定流量频率和减轻强迫振动的潜力。

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引用次数: 0

Mechanism analysis of the effect of the slot and the air-entraining jet on the evolution of compressor vortex structure 狭缝和引气射流对压气机涡结构演化影响的机理分析

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-01-06 DOI: 10.1016/j.ast.2026.111647

Wenfeng Xu, Shilong Zou, Shengyuan Wang, Guozhe Ren, Huan Zhao, Xin Sui

The interstage leakage flow is one of the main reasons for the blockage of the compressor passage. The blade root slot structure(SJ) can effectively blow away low-energy fluid. Inspired by this, the team designed the air-entraining jet structure (AEJ), where the jet is formed by high-pressure air flow in the sealing cavity. It is of great practical significance to compare it with existing flow control technology and then explore the mechanisms of the two approaches to improve the flow field structure. Under different inflow Mach numbers, both schemes demonstrate the improvement of the flow field, and the improvement effect decreases with increasing Mach number. At 0.5 Ma, the two schemes lower the loss by 21.5% and 10.6%, respectively. As the incidence angle rises, the loss of all schemes initially decreases and then increases. Among them, SJ and AEJ exhibit the minimum loss at -2°, and the improvement effect is observed at this angle. The improvement effect of SJ gradually decreases as the incidence angle rises. In contrast, the improvement effect of AEJ increases first and then decreases. The primary difference between the two schemes lies in the blade root slot structure, which significantly compresses the passage vortex with negative vorticity and reduces the separation height by ejecting high-velocity airflow into the passage vortex. The jet velocity of AEJ is low, which does not significantly influence the passage vortex, but only decreases in the pitchwise direction. The advantage of AEJ is that it does not considerably enhance the transverse secondary flow of the end wall.

级间泄漏流是造成压缩机通道堵塞的主要原因之一。叶根槽结构（SJ）可以有效地吹走低能流体。受此启发，该团队设计了吸气射流结构（AEJ），其中射流由密封腔中的高压气流形成。将其与现有的流动控制技术进行比较，进而探讨两种方法改善流场结构的机理，具有重要的现实意义。在不同的来流马赫数下，两种方案均能改善流场，但改善效果随马赫数的增加而降低。在0.5 Ma时，两种方案的损耗分别降低了21.5%和10.6%。随着入射角的增大，各方案的损耗先减小后增大。其中，SJ和AEJ在-2°时损失最小，在该角度下有明显的改善效果。随着入射角的增大，SJ的改善效果逐渐降低。相反，AEJ的改善效果先增大后减小。两种方案的主要区别在于叶根槽结构，通过向通道涡中喷射高速气流，显著压缩负涡量的通道涡，降低分离高度。AEJ的射流速度较低，对通道涡的影响不显著，仅在俯仰方向上减小。AEJ的优点是它不会显著增强端壁的横向二次流。

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引用次数: 0